Detonation engine and flying object provided therewith

Abstract

A detonation engine which creates thrust by generating a detonation wave, wherein the overall engine structure is simplified, and continuous output can be obtained, comprises: a rotational flow generation device which generates rotational flow about an axis in a mixed gas of air and fuel or of oxygen and fuel; a detonation chamber arranged downstream from the rotational flow generation device, formed in a ring-shape radially extended and continuous in the circumferential direction, which continuously combusts in the circumferential direction the mixed gas in which the rotational flow is generated to generate detonation waves, and draws it in from the radial inside and exhausts it to the radial outside; and a nozzle which is connected to the detonation chamber, and jets the high temperature and pressure combustion gas generated by the detonation waves flowing from the detonation chamber, to the rear while expanding it, and converts it into thrust.

1. A detonation engine comprising: a plurality of guide vanes which generate a circumferential rotational flow in a mixed gas of air and fuel or a mixed gas of oxygen and fuel about a centerline axis; at least one fuel injector arranged upstream of said guide vanes, with respect to the flow of the mixed gas; a detonation chamber which is arranged on a downstream and radially outward side of said guide vanes, formed in a ring-shape that is radially extended and continuous in a circumferential direction, in which detonation waves and a combustion gas at a high temperature and under a high pressure that continuously flow in an outward radial direction, with respect to the centerline axis through the detonation chamber, are generated by combusting the mixed gas in which the circumferential rotational flow is generated by said plurality of guide vanes; and a nozzle connected to said detonation chamber that discharges the detonation waves to the rear, expands the combustion gas, and converts the combustion gas into thrust, the combustion gas flowing continuously to the rear while rotating. 
   
   
     2. A detonation engine according to  claim 1 , further comprising:
 an outer casing located radially outside of said plurality of guide vanes, said detonation chamber, and said nozzle with a space therebetween so as to surround said guide vanes, said detonation chamber, and said nozzle, wherein a bypass passage is formed by the space between said outer casing and said plurality of guide vanes, said detonation chamber, and said nozzle. 
 
   
   
     3. A flying object comprising the detonation engine according to  claim 1 . 
   
   
     4. A detonation engine comprising: an impeller which generates a circumferential rotational flow in a mixed gas of air and fuel or a mixed gas of oxygen and fuel about a centerline axis; at least one fuel injector arranged upstream of said impeller, with respect to the flow of the mixed gas; a detonation chamber which is arranged on a downstream and radially outward side of said impeller, formed in a ring-shape that is radially extended and continuous in a circumferential direction, in which detonation waves and a combustion gas at a high temperature and under a high pressure that continuously flow in an outward radial direction, with respect to the centerline axis through the detonation chamber, are generated by combusting the mixed gas in which the circumferential rotational flow is generated by said impeller, the combustion gas flowing continuously to the rear while rotating; a turbine rotor having a shaft, a disk, an impeller, and a plurality of turbine blades, said turbine blades attached to said shaft via said disk; and a turbine nozzle comprising a plurality of nozzle guide vanes having an airfoil cross section which are arranged annularly, so as to expand and decompress the gas flowing out from said detonation chamber, and cause the gas flowing out from said turbine nozzle to impinge on said turbine blades at an appropriate angle wherein said turbine blades, said shaft, said impeller and said disk rotate together as one. 
   
   
     5. A flying object comprising a detonation engine, said detonation engine comprising: a plurality of guide vanes which generate a circumferential rotational flow in a mixed gas of air and fuel or a mixed gas of oxygen and fuel about a centerline axis; at least one fuel injector arranged upstream of said guide vanes, with respect to the flow of the mixed gas; a detonation chamber which is arranged on a downstream and radially outward side of said plurality of guide vanes, formed in a ring-shape that is radially extended and continuous in a circumferential direction, in which detonation waves and a combustion gas at a high temperature and a high pressure that continuously flow in an outward radial direction, with respect to the centerline axis through the detonation chamber, are generated by combusting the mixed gas in which the circumferential rotational flow is generated by said plurality of guide vanes; a turbine rotor comprising: a disk attached via a bearing so as to cover a main body of said detonation engine; a plurality of turbine blades located on said disk, said turbine blades being rotated by impingement of gas flowing out from said detonation chamber; and a fan located on said turbine blades; a nozzle arranged on a downstream side of said turbine rotor that discharges the detonation waves to the rear, expands the combustion gas, and converts the combustion gas into thrust, the combustion gas flowing continuously to the rear while rotating; and an outer casing located radially outside of said guide vanes, said detonation chamber, and said nozzle with a space therebetween so as to surround said guide vanes, said detonation chamber, and said nozzle, wherein a bypass passage is formed by the space between said outer casing and said guide vanes, said detonation chamber, and said nozzle.